EP0188823B1 - Abschlussvorrichtung für eine Flügelfläche - Google Patents
Abschlussvorrichtung für eine Flügelfläche Download PDFInfo
- Publication number
- EP0188823B1 EP0188823B1 EP85201286A EP85201286A EP0188823B1 EP 0188823 B1 EP0188823 B1 EP 0188823B1 EP 85201286 A EP85201286 A EP 85201286A EP 85201286 A EP85201286 A EP 85201286A EP 0188823 B1 EP0188823 B1 EP 0188823B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- door
- airfoil
- leading edge
- opening
- connecting member
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 230000000694 effects Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 2
- 239000012858 resilient material Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
Definitions
- the invention relates to an airfoil as defined in the introductory part of claim 1.
- Aircraft wings are commonly designed with leading edge flaps or slats which have a retracted position for cruise, and a downwardly and forwardly extended position for high lift operation, such as in takeoff and landing.
- the flaps or slats In the cruise configuration, the flaps or slats generally conceal the main or fixed leading edge structure of the airfoil, but in the deployed position, the surface of this leading edge structure of the airfoil is exposed to airflow, in circumstances where, for example, the flap or slat forms with the main leading edge structure a slot for flow of air therethrough.
- connecting member extending between the flap and the wing structure, such as a track which supports the flap, or a servicing member such as a telescopic thermal anti-icing duct.
- interconnecting members In some circumstances, it is necessary for these interconnecting members to penetrate (i.e. extend) through the skin forming the leading edge surface of the main airfoil structure.
- An airfoil structure of this kind is known from GB-A-I 572 004.
- the means for closing the opening are formed by an annular seal of resilient material.
- the invention has for its object to provide an airfoil of the kind set forth above, in which the opening formed in the front skin section can adequately be closed, specifically when the connecting member has a component of motion in said opening generally transverse to the chord- wise axis.
- the track 18 is formed in a moderate curve. Further, the forward end 24 of the track 18 extends moderately upwardly from the forward portion of the main curved portion of the track 18. With this particular arrangement, as the track 18 moves from the position of Figure 1 to the positions of Figure 2, the motion of the track is such that the track 18 has not only a forward but a downward component of motion in a vertical plane generally parallel to the cordwise axis of the wing 10.
- the opening 42 can be considered as having a forward opening portion 42a which curves from a lower location upwardly past the forwardmost portion of the forward skin portion 38 and upwardly therefrom a short distance in the upwardly and rearwardly curved portion of the skin portion 38.
- the lower rear opening portion 42b extends essentially horizontally rearwardly.
- this door assembly 54 is particularly adapted to close the forward opening portion 42a in a particularly convenient and effective manner so as to be compatible with the configuration and operating characteristics of the components described above.
- This door assembly 54 comprises a door member 56 and a mounting device 58 by which the door member 56 is mounted for rotation from a first retracted position illustrated at 56a in Figure 6) to a second deployed position (illustrated at 56b in Figure 6).
- the door member 56 is curved to match the general configuration of the forward skin portion 38.
- the door member 56 comprises a middle forward portion 60, a downwardly and rearwardly curving lower portion 62, and an upwardly and rearwardly curving upper portion 64.
- the perimeter portion of the door member 56 extends moderately beyond the edge openings 46 and 44 so as to fit against a perimeter portion 66 of the skin section 38, which perimeter portion 66 defines the opening portion 42a.
- the mounting device 58 is essentially a spring loaded hinge assembly comprising a first arm 68 fixedy attached to the inner surface of the skin portion 38, and a second swing arm 70 fixedly attached to the inner surface of the lower portion 62 of the door member 56.
- the hinge connection of the arms 68 and 70 is or may be conventional and is designated 72.
- a spring member 74 has a middle coil portion 76 wrapped around the hinge portion 72, and two spring arms 78 and 80 reacting against the arms 68 and 70, respectively. The action of the spring member 74 is such that it urges the swing arm 70 and the door member 56 downwardly and forwardly to the deployed position at 56b where the door member 56 closes the front opening portion 42a.
- the door assembly 54 is particularly arranged to function in the rather limited space which exists between the skin portion 38 and the web 52 of the front spar 50.
- the axis of rotation 82 provided by the hinge mechanism 72 is arranged so that it extends upwardly and forwardly, so as to be generally positioned in (i.e. have substantial alignment components parallel to) a vertical plane which is generally parallel to a vertical plane through which the main track 18 moves between its retracted and deployed positions. Further, this axis of rotation 82 is spaced laterally in a spanwise direction from the plane of motion within which the main track 18 moves.
- this axis of rotation 82 has a substantial component of alignment that is generally perpen- dicularto a plane occupied by an upper portion 84 of the forward skin section 38, the portion 84 being that part of the skin section 38 which the door 56 moves adjacent to and generally parallel with, in moving from its deployed position 56b to its retracted position 56a.
- the axis of rotation 82 should have a substantial component of alignment generally perpendicular to the plane occupied by the upper skin portion 84, this being the skin portion which the door member 56 moves adjacent to as it moves to its deployed position 56a. Further, as indicated previously, the axis of rotation 82 should have a substantial-component of alignment which lie in a vertical plane which is generally parallel to a vertical plane in which the main track 18 moves in travelling between its retracted position to its deployed positions 14a or 14b.
- the axis of rotation 82 could deviate to some extent from these alignment limitations, depending upon the geometry and configuration of the surrounding structure.
- the present invention has been shown used with a track 18, it is to be understood that it could be used with other components where similar problems exist, such as a service connection (e.g. a telescoping tube) which would provide de- icing for the leading edge slat.
- a service connection e.g. a telescoping tube
- leading edge is, within the broader scope of the present invention, intended to refer to a trailing edge configuration where like problems may exist.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
Claims (8)
wobei die Mittel zum Schließen der Öffnung folgendes umfassen:
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US687929 | 1984-12-31 | ||
US06/687,929 US4640477A (en) | 1984-12-31 | 1984-12-31 | Closing device for an airfoil |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0188823A1 EP0188823A1 (de) | 1986-07-30 |
EP0188823B1 true EP0188823B1 (de) | 1988-10-19 |
Family
ID=24762434
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP85201286A Expired EP0188823B1 (de) | 1984-12-31 | 1985-08-08 | Abschlussvorrichtung für eine Flügelfläche |
Country Status (3)
Country | Link |
---|---|
US (1) | US4640477A (de) |
EP (1) | EP0188823B1 (de) |
DE (1) | DE3565660D1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11845550B2 (en) | 2019-02-28 | 2023-12-19 | Airbus Operations Gmbh | Wing leading-edge device and a wing having such a wing leading-edge device |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2204538B (en) * | 1987-05-06 | 1990-12-12 | British Aerospace | Wing leading edge arrangements for aircraft |
GB8729655D0 (en) * | 1987-12-19 | 1988-02-03 | British Aerospace | Wing leading edge arrangements for aircraft |
US4838502A (en) * | 1988-03-16 | 1989-06-13 | The Boeing Company | Resiliently deployable fairing for sealing an airframe cavity |
GB8910654D0 (en) * | 1989-05-09 | 1989-06-21 | British Aerospace | Flexible closing device for a wing leading edge |
GB9607707D0 (en) * | 1996-04-13 | 1996-06-19 | Broadbent Michael C | A self-sealing parallelogram slat mechanism |
US6015117A (en) * | 1996-04-13 | 2000-01-18 | Broadbent; Michael C | Variable camber wing mechanism |
US5927656A (en) * | 1996-06-26 | 1999-07-27 | The Boeing Company | Wing leading edge flap and method therefor |
DE19925560B4 (de) | 1999-06-04 | 2004-04-22 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Zusatzflügel für Hauptflügel von Flugzeugen |
GB0114634D0 (en) | 2001-06-15 | 2001-08-08 | Broadbent Michael C | Contiguous variable camber device |
US7249735B2 (en) * | 2005-06-30 | 2007-07-31 | The Boeing Company | Translating conduit apparatus for an airplane or equipment |
GB0722425D0 (en) * | 2007-11-15 | 2007-12-27 | Airbus Uk Ltd | Slat support funk plate |
GB201008773D0 (en) * | 2010-05-26 | 2010-07-14 | Airbus Uk Ltd | Aircraft slat assembly |
US8622350B1 (en) * | 2011-11-14 | 2014-01-07 | The Boeing Company | Compound leading edge device for aircraft |
US9296464B1 (en) * | 2014-11-12 | 2016-03-29 | The Boeing Company | Aircraft and associated door member biasing assembly and method |
GB2533311A (en) * | 2014-12-15 | 2016-06-22 | Airbus Operations Ltd | A track container |
US9937999B2 (en) * | 2015-06-01 | 2018-04-10 | Northrop Grumman Systems Corporation | Deployable propeller |
US11192625B2 (en) | 2016-06-17 | 2021-12-07 | Bombardier Inc. | Panels for obstructing air flow through apertures in an aircraft wing |
US11713106B2 (en) * | 2019-03-26 | 2023-08-01 | Embraer S.A. | Articulated cover assembly for wing leading edge slat telescopic tube duct |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2381680A (en) * | 1940-11-12 | 1945-08-07 | Frank R Maxwell | Airplane and control device therefor |
US2381679A (en) * | 1940-11-12 | 1945-08-07 | Frank R Maxwell | Airplane and control device therefor |
FR1011175A (fr) * | 1948-12-20 | 1952-06-19 | Onera (Off Nat Aerospatiale) | Perfectionnement aux ailes d'avions |
GB1070723A (en) * | 1963-01-16 | 1967-06-01 | Dehavilland Aircraft | Improvements in or relating to aircraft |
US3680815A (en) * | 1967-06-14 | 1972-08-01 | Avions Marcel Dassult | Obturator for openings formed in aircraft fairings |
US3968946A (en) * | 1975-03-31 | 1976-07-13 | The Boeing Company | Extendable aerodynamic fairing |
US4042191A (en) * | 1976-05-03 | 1977-08-16 | The Boeing Company | Slot seal for leading edge flap |
US4189121A (en) * | 1978-01-23 | 1980-02-19 | Boeing Commercial Airplane Company | Variable twist leading edge flap |
GB1572004A (en) * | 1978-03-30 | 1980-07-23 | Hawker Siddeley Aviation Ltd | Aircraft wings |
US4360176A (en) * | 1979-11-05 | 1982-11-23 | The Boeing Company | Wing leading edge slat |
-
1984
- 1984-12-31 US US06/687,929 patent/US4640477A/en not_active Expired - Fee Related
-
1985
- 1985-08-08 EP EP85201286A patent/EP0188823B1/de not_active Expired
- 1985-08-08 DE DE8585201286T patent/DE3565660D1/de not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11845550B2 (en) | 2019-02-28 | 2023-12-19 | Airbus Operations Gmbh | Wing leading-edge device and a wing having such a wing leading-edge device |
Also Published As
Publication number | Publication date |
---|---|
EP0188823A1 (de) | 1986-07-30 |
US4640477A (en) | 1987-02-03 |
DE3565660D1 (en) | 1988-11-24 |
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